J-GLOBAL ID:200904005383425159  Research Project code:9800042457 Update date:Feb. 29, 2000

Study on experiment and numerical calculation of mixing in supersonic flow

Study period:1995 - 1997
Organization (1):
Investigating Researcher (1):
Research overview:
The scramjet, a propellant system for supersonic or hypersonic flight vehicles, develops air intake, fuel mixing, and nozzle exhaust at supersonic speeds. An important problem is how to rapidly mix the fuel into the supersonic air flow. To examine the profile and mechanism of mixing and flow distribution, this study carries out (1) vertical injection into high-speed air flow of mach 4 from a circular nozzle, and (2) parallel injection using a ramp type injector.
Keywords (6):
supersonic ,  scramjet ,  wind ,  fuel ,  mixing ,  flow
Research program: Ordinary Research
Ministry with control over the research :
Ministry of Education, Culture, Sports, Science and Technology

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